Axial turbomachine with low tip clearance losses

F - Mech Eng,Light,Heat,Weapons – 01 – D

Patent

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Details

F01D 5/20 (2006.01) F01D 5/14 (2006.01) F01D 11/08 (2006.01)

Patent

CA 2731092

An axial turbo engine (1), comprises an impeller blade array, made up of impeller blades (3) each with a front edge (8), a radially outer free blade tip (15) and an annular enclosure (13) enclosing the impeller blade array with an annulus inner side (14) by means of which the annular enclosure (13) is arranged directly adjacent to the blade tips (15) to give a radial gap (16) between the enveloping ends of the blade tips (15) and the annulus inner side (14), wherein the impeller blades (3) have a radial projection (18) in the region of the front edge (8) thereof on the blade tip (15) and the annular enclosure (13) has an annular radial recess (17) in the annulus inner side (14) thereof, arranged at a radial distance (16) from the enveloping ends of the blade tips (15), such that in the main flow direction of the axial turbo engine (1) the line of the radial projections on the side thereof facing the radial gap (16) matches the line of the radial recess.

L'invention concerne une turbomachine axiale (1) comprenant une grille d'aubes formée d'aubes (3) comprenant chacune un bord d'attaque (8) et un sommet (15) libre située radialement à l'extérieur, et une paroi (13) délimitant un espace annulaire recouvrant la grille d'aubes, et comprenant une face interne (14) d'espace annulaire, la paroi d'espace annulaire (13) étant placée à proximité immédiate des sommets (15) des aubes de telle manière qu'un espace radial (16) est formé entre les courbes enveloppes des sommets d'aubes (15) et la face interne de la paroi annulaire (14). Les aubes (3) présentent sur leurs sommets (15), dans la zone de leur bord d'attaque (8), une élévation radiale (18) respective, et la paroi d'espace annulaire (13) présente de manière similaire un enfoncement radial (17) circulaire sur sa face interne (14), espacé radialement (16) des courbes enveloppes des sommets d'aubes (15), de telle manière que dans la direction d'écoulement principale de la turbomachine axiale (1), le parcours des élévations radiales, au niveau de leurs côtés orientés vers l'espace radial (16), correspond au parcours des enfoncements radiaux.

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